FR2405367A1 - COMBINED GAS TURBINE FOR FLYING MACHINES WITH V / STOL CHARACTERISTICS - Google Patents

COMBINED GAS TURBINE FOR FLYING MACHINES WITH V / STOL CHARACTERISTICS

Info

Publication number
FR2405367A1
FR2405367A1 FR7828663A FR7828663A FR2405367A1 FR 2405367 A1 FR2405367 A1 FR 2405367A1 FR 7828663 A FR7828663 A FR 7828663A FR 7828663 A FR7828663 A FR 7828663A FR 2405367 A1 FR2405367 A1 FR 2405367A1
Authority
FR
France
Prior art keywords
gas turbine
combined gas
precompressor
flying machines
stol characteristics
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
FR7828663A
Other languages
French (fr)
Other versions
FR2405367B3 (en
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of FR2405367A1 publication Critical patent/FR2405367A1/en
Application granted granted Critical
Publication of FR2405367B3 publication Critical patent/FR2405367B3/fr
Granted legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Abstract

a. Turbine à gaz combinée pour engin volant ayant des caractéristiques V/STOL. b. Moteur caractérisé en ce qu'un précompresseur est prévu entre le compresseur et la machine soufflante, ce précompresseur, traversé par le canal annulaire, étant couplé à au moins un étage de la turbine par un arbre d'entraînement qui entraîne au choix le précompresseur et le dispositif de sustentation ou la machine soufflante. c. L'invention s'applique notamment aux moteurs d'hélicoptères.at. Combined gas turbine for flying machine with V / STOL characteristics. b. Engine characterized in that a precompressor is provided between the compressor and the blower machine, this precompressor, through which the annular channel passes, being coupled to at least one stage of the turbine by a drive shaft which drives the precompressor as desired and the lifting device or the blowing machine. vs. The invention applies in particular to helicopter engines.

FR7828663A 1977-10-07 1978-10-06 COMBINED GAS TURBINE FOR FLYING MACHINES WITH V / STOL CHARACTERISTICS Granted FR2405367A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19772745131 DE2745131A1 (en) 1977-10-07 1977-10-07 COMBINATION GAS TURBINE ENGINE FOR AIRCRAFT WITH V / STOL PROPERTIES

Publications (2)

Publication Number Publication Date
FR2405367A1 true FR2405367A1 (en) 1979-05-04
FR2405367B3 FR2405367B3 (en) 1981-07-31

Family

ID=6020902

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7828663A Granted FR2405367A1 (en) 1977-10-07 1978-10-06 COMBINED GAS TURBINE FOR FLYING MACHINES WITH V / STOL CHARACTERISTICS

Country Status (4)

Country Link
US (1) US4214440A (en)
DE (1) DE2745131A1 (en)
FR (1) FR2405367A1 (en)
GB (1) GB2005356B (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2445439A1 (en) * 1978-12-27 1980-07-25 Gen Electric IMPROVED TURBOCHARGER ENGINE
EP2435685A1 (en) * 2009-05-27 2012-04-04 Turbomeca Turbine engine comprising an exhaust-gas guide cone with a sound suppressor
WO2016151236A1 (en) 2015-03-26 2016-09-29 Safran Aircraft Engines Aircraft turbine engine with planetary or epicyclic gear train
WO2017203155A1 (en) 2016-05-24 2017-11-30 Safran Helicopter Engines Aircraft turbine engine with epicyclic reduction gear having a variable reduction ratio

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4791783A (en) * 1981-11-27 1988-12-20 General Electric Company Convertible aircraft engine
US4543036A (en) * 1981-12-22 1985-09-24 The Garrett Corporation Fluid compressor control and operation
US4461145A (en) * 1982-10-08 1984-07-24 The United States Of America As Represented By The Secretary Of The Air Force Stall elimination and restart enhancement device
US4598544A (en) * 1983-04-28 1986-07-08 Williams International Corporation Medium bypass turbofan engine
US4640153A (en) * 1983-12-09 1987-02-03 Teledyne Industries, Inc. Accessory drive for a turbine engine
EP0156933B1 (en) * 1984-04-02 1987-11-19 The Boeing Company Turboprop engine
FR2593237B1 (en) * 1986-01-17 1989-09-01 Hispano Suiza Sa COLD FLOW CHANNEL OF MULTI-FLOW TURBOREACTOR DRIVE INVERTER ASSOCIATED WITH COMBINED AIR TAKE-OFF MEANS
DE3911715A1 (en) * 1989-04-10 1990-10-11 Mtu Muenchen Gmbh SHUT-OFF DEVICE FOR BLOWED, IN PARTICULAR BLOWED, RADIANT JET ENGINES
US5150567A (en) * 1989-06-05 1992-09-29 General Electric Company Gas turbine powerplant
US5228349A (en) * 1990-09-18 1993-07-20 Simmonds Precision Products, Inc. Composite power shaft with intrinsic parameter measurability
US7832193B2 (en) * 2006-10-27 2010-11-16 General Electric Company Gas turbine engine assembly and methods of assembling same
US20110167792A1 (en) * 2009-09-25 2011-07-14 James Edward Johnson Adaptive engine
US20110167791A1 (en) * 2009-09-25 2011-07-14 James Edward Johnson Convertible fan engine
US20110167831A1 (en) * 2009-09-25 2011-07-14 James Edward Johnson Adaptive core engine
CA2819586C (en) * 2010-12-10 2014-09-16 Corporation Mc2 Recherches Internationales Turbine assembly, and kit with components for assembling the same
US20120275921A1 (en) * 2011-04-28 2012-11-01 General Electric Company Turbine engine and load reduction device thereof
WO2014055122A1 (en) * 2012-10-01 2014-04-10 United Technologies Corporation Geared turbofan high gearbox power density
US10329943B2 (en) 2014-11-18 2019-06-25 Rolls-Royce North American Technologies Inc. Split axial-centrifugal compressor
US9982676B2 (en) * 2014-11-18 2018-05-29 Rolls-Royce North American Technologies Inc. Split axial-centrifugal compressor
US10794281B2 (en) 2016-02-02 2020-10-06 General Electric Company Gas turbine engine having instrumented airflow path components
US11073090B2 (en) 2016-03-30 2021-07-27 General Electric Company Valved airflow passage assembly for adjusting airflow distortion in gas turbine engine
US10753278B2 (en) * 2016-03-30 2020-08-25 General Electric Company Translating inlet for adjusting airflow distortion in gas turbine engine
EP3444495A1 (en) 2017-08-18 2019-02-20 Rolls-Royce Deutschland Ltd & Co KG Mechanical clutch device and method for operating a mechanical clutch device
US10954813B2 (en) 2017-08-18 2021-03-23 Rolls-Royce Deutschland Ltd & Co Kg Planetary gearbox system and method for operating a planetary gearbox system
US11267579B2 (en) * 2019-03-26 2022-03-08 Textron Innovations Inc. Compound helicopters having hybrid propulsion engines

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2737018A (en) * 1950-07-01 1956-03-06 Gen Motors Corp Propeller brake system
US2803943A (en) * 1953-12-30 1957-08-27 Armstrong Siddeley Motors Ltd Means for supporting and driving accessories which are exterior to a ductedfan turbo-jet engine
US2981063A (en) * 1957-06-17 1961-04-25 Wickman Axel Charles Variable speed power transmission mechanisms
US3381474A (en) * 1966-06-10 1968-05-07 Gen Electric Compound aircraft and propulsion system
US3678690A (en) * 1970-07-10 1972-07-25 United Aircraft Corp Convertible composite engine
US3792586A (en) * 1973-01-22 1974-02-19 Avco Corp Bearing assembly systems

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2445439A1 (en) * 1978-12-27 1980-07-25 Gen Electric IMPROVED TURBOCHARGER ENGINE
EP2435685A1 (en) * 2009-05-27 2012-04-04 Turbomeca Turbine engine comprising an exhaust-gas guide cone with a sound suppressor
EP2435685B1 (en) * 2009-05-27 2017-03-29 Safran Helicopter Engines Gas turbine engine comprising exhaust cone with integrated muffler
WO2016151236A1 (en) 2015-03-26 2016-09-29 Safran Aircraft Engines Aircraft turbine engine with planetary or epicyclic gear train
FR3034140A1 (en) * 2015-03-26 2016-09-30 Snecma AIRCRAFT TURBOMACHINE WITH PLANETARY OR EPICYCLOIDAL REDUCER
US11047252B2 (en) 2015-03-26 2021-06-29 Safran Aircraft Engines Aircraft turbine engine with planetary or epicyclic gear train
WO2017203155A1 (en) 2016-05-24 2017-11-30 Safran Helicopter Engines Aircraft turbine engine with epicyclic reduction gear having a variable reduction ratio

Also Published As

Publication number Publication date
DE2745131A1 (en) 1979-04-12
FR2405367B3 (en) 1981-07-31
GB2005356B (en) 1982-03-31
US4214440A (en) 1980-07-29
GB2005356A (en) 1979-04-19

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Legal Events

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ST Notification of lapse